Aircraft



C. S. HALL AIRCRAFT Original Filed March 25, 1924 Czar/es .5. Ha

IN V EN TOR.

ATTORNEY.

Patented Dec. 27, 1927.

UNITED-STATES- CHARLES S.- HALL, LOS ANGELES, G AIJIFOBNI A, ASSIGNOR TOIHALL AIRWAYS COR- PORTION, OF DOVER, DELAWARE, A CORPORATION.

4 Application filed March 25, 1924, Serial No. 701,733. Renewed February 2, 1926.

My invention relates to aircraft 'of the dirigible type, particularly of the rigid type of construction,and has for its main ob ect to provide a series of compartments having a relatively smooth inner surface wherein as riggers, to constantly watch for anyundue stresses upon the gas container by reason of the varying sizes and stresses of the gas container at various altitudes.

In the present evolvement, a telescoping portion is arranged in conjunction with the gas containing envelope, the said telescoping portion carrying. a diaphragm, thus providing a comparatively w rig-id envelope while the telescoping or collapsing portion will take care of the varying pressures and at the same time this telescoping portion will be comparatively free from entanglements and makepossible its upper and downward movement at all times.

Another object is to provide a means of constructing the major portion of the gas containing envelope of non-porous material, such as metal, so that the process of osmosis will be eliminated or reduced to the least possible efie'cts.

Another object is to provide a construc-v tion which will avoid, or reduce, as much as possible, the dangers and losses due to osmosis, since it is generally recognized in :the art that, with hydrogen as a levitating element, the impurities are generally found at the lower part of the container, while the osmosis takes place more rapidly at the surface of highest pressure, which is, of course, at the top of the container, and thus by making the upper-part of non-porous or impervious material, such as metal, or other suitable element, the dangers of explosion of hydrogen due to impurities, occasioned by osmosis, will be reduced or eliminated, or if helium is used, excessive and costly losses will be avoided bythe same means. My invention eliminates excessive costs of operation and avoids delays occasioned by necessity or refilling the containers. My invention also reduces the costs of operations due to the reduced lifting capacity of the levitating element.

. this specification but which are used'for illine 3-3 in- Figure 2.

1,653,902 PATENT OFFICE.

Having thus described the main objects of my invention I will now describe the same with reference to the accompanying drawings which form an essential part of lustration only.

Figure 1 is a. side. view of the aircraft with the central portion of'the outer covering and a portionof the framework removed.

Figure 2 is a cross-sectional view taken on line 2-2 looking in the direction indicated by the arrows thereon. I

Figure 3 is a longitudinal section drawn through one of the compartments looking T0 in the direction indicated by the arrows of In carrying .out my invention as shown and illustrated in the accompanying drawings, in its preferred form, a body, or framework, 1 is provided and an outer covering 2 is arranged thereon. Within the said framework '21 series of compartments C are arranged, the inner surfaces of which are made relatively smooth. Between the said compartment walls the framework 1 is transversely arranged, as can be readily understood. l/Vithin the compartment C a gas containing envelope 3, made of impervious material, such as metal, is arranged. The lower margin of the said envelope 3 is provided with a framework 4 carrying collapsible element 5 on which diaphragm 6 is arranged.

a Now it will be seen that when container 3 isfilled with a levitating element under atmosphericj pressure the collapsing element 5 carrying diaphragm 6 is close underneath the said framework 4, but as the aircraft ascends, involving a decrease in pressure of the atmosphere entailing a relative ;increase in the volume of the levitating element in order to maintain equi-stati'c pressures on either side of the dlaphragm, the collapsin element 5 automatically varies the position of the said diaphragm, as can be readily understood.

Of course, it is understood that the collapsing element will be made of flexible material, such as rubberized si1k, or even of rubber, and that the said container 3 may be connected with other containersby means of tube 7 and valve 8, as shown in Figure 3, through which the air may be discharged or the gas inserted during thefilling and operating' of the craft. Also by means of a flexible tube 9 and valve 10 the container may be inflated or deflated.

The body or hull 1 is provided with superimposed compartments or chambers. comprise the upper compartment or chamber 3 previously mentioned, the intermediate compartment or chamber 12, which is provided with windows 13, and a floor lion which seats are mounted. Beneath the floor 14 is a lower chamber or compartment 16. These chambers extend longitudinally and transversely of the body as shown.

Having thus described my invention in its preferred form, I claim:

1. In an aircraft having a gas containing element, the combination of; a gas container arranged within a compartment provided in the said aircraft, the said gas container being constructed of impervious material and of a form substantially coinciding with the inner surface of the said compartment; a frame arranged onthe said container; and

a diaphragm carried on the said frame, the

said diaphragm carried by a collapsible element, substantially as described.

2. In an aircraft, the combination of; a bgdy framework; a covering therefor; a series of compartments of relatively smooth inner surfaces arranged in the said body; and a gas container arranged within the 4 said compartment, the said gas container having a collapsible element associated therewith, the said collapsibleelement having a diaphragm arranged therewith and carried thereon and freely exposed on one side to the atmosphere whereby the collapsible element will automatically vary the position of said diaphragm to equalize the pressures on opposite sides thereof at all altitudes, for the purposes described.

3. In an aircraft, the combiantion of; a framework; an outer covering arranged on the said framework; a series of compartments arranged within the said framework, the said compartments having relatively smooth inner walls, a gas containing envclope arranged within the said compartment and substantially of the form thereof, the said envelope having a framework associated therewith carrying a collapsible element attached thereto; and a diaphragm carried upon the said collapsible element,

These and having its outer face open freely to the atmosphere, whereby pressures are automatically equalized on opposite sides thereof,

envelopes are encased, said aircraft having an outer covering thereon.

5. In an aircraft, the combination of; a.

body; compartments arranged within the said body; gas containing envelopes arranged within the said compartments; a col lapsible element carried by and; in free communication interiorly with the said envelope; and a diaphragm carried by the said collapsible element, said diaphragm being open to the atmosphere on its outer side whereby pressures are automatically equalizedon opposite sides thereof, substantially as disclosed.

. 6, In a gas container for aircraft, the combination of; a collapsible element formed as a continuation of and in freely-open communication with the said container; and a diaphragm carried by the said collapsible.

element, substantially as disclosed.

7. In a gas container for aircraft, the combination of; an envelope; a collapsible element formed as a continuation of and in freely-open communication with the said envelope; and a diaphragm carriedby the said collapsible element, substantially as dis closed.

8. In an aircraft, the combination of a framework, a plurality of longitudinally arranged gas containing envelopes of ri material enclosed thereby, each having a freely open end, a collapsible chamber secured to andopening into said end, and a diaphragm closing the opposite end of said chamber with its outer side exposed to atmospheric pressure.

In testimony whereof I have signed my name to this specification.

CHARLES S. HALL. 

